@A310

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 22

TITLE: AUTO FLIGHT - GENERAL - ACTIVATE STOP RUDDER INPUT

WARNING DEVICE

MODIFICATION No.: 13593S22853

This page transmits Revision No.01 of Service Bulletin No.A310-22-2064

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to add aircraft for operator FDX.

CHANGES

SUMMARY

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

R

MANPOWER MANPOWER UPDATED R

WEIGHT AND BALANCE Minor editorial or document structure change R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

LIST OF COMPONENTS

Kit 222064A01R01 PART MATERIAL SET UPDATED

MATERIAL SET LABEL UPDATED

QUANTITY UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 222064- 831-801-001-Modification

Subtask 222064-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 222064-831-001-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

MATERIAL LIST UPDATED

R

Subtask 222064-831-002-001 SUBTASK SOLUTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 222064-700-001-001 SUBTASK SOLUTION UPDATED R

Subtask 222064-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Fig. A-FBAAA FIGURE SOLUTION UPDATED R

Fig. A-FBAAA Sheet 01 SHEET UPDATED R

Fig. A-FBAAA Sheet 02 SHEET UPDATED R

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Nov 18/11

REVISION No. : 01 - May 31/12

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 2

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SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 22

TITLE: AUTO FLIGHT - GENERAL - ACTIVATE STOP RUDDER INPUT

WARNING DEVICE

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR 13593S22853

MINOR None

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

This Service Bulletin is issued further to an operator’s request.

Following report of events of excessive rapid alternating and large rudder pedal inputs that resulted in

high vertical stabilizer loads, this service bulletin provides increased protection by improvement of the

cockpit crew awareness in case of excessive rudder reversal control input.

This is achieved by activation of a warning red light "STOP" on rudder input panels in front of each pilot

which is reinforced by an aural warning "Stop rudder input".

This Service Bulletin installs on Captain and First Officer (F/O) side new 510VU including a red lighted

push-button and activates the function.

Aircraft have to be previously equipped with :

- System and mechanical provision

- Flight Warning Computer (FWC) STD S17 P/N 35-0B5-3008-320

- Flight Control Computer (FCC) P/N B470ADM03

Accomplishment of this Service Bulletin will satisfy the operator’s request.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 1

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SERVICE BULLETIN

SUMMARY

The Operational/Maintenance Consequences of this Service Bulletin are covered by the update of the

affected publications detailed in PLANNING INFORMATION

NOTE: Accomplishment of this Service Bulletin requires previously a crew training to familiarize

flight crew with the warning and the associated procedures.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED YES

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 222064A01R01 1 See SB Panels, Contacts

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

99Y FDX

NOTE: This Service Bulletin is written for the operators listed above. The modification in this

Service Bulletin can be done by other operators. If other operators want to do this

modification, use the RFC/RMO procedure and write to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

SC Department

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the

following Service Bulletins :

Service Bulletin No. A310-22-2063

A310-22-2065

A310-31-2144

NOTE: Accomplishment of this Service Bulletin requires previously a crew training to familiarize

flight crew with the warning and the associated procedures.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 2

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@A310

SERVICE BULLETIN

SUMMARY

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT YES

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 222064-831-801-001: Modification

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 4.00

APPENDICES

Appendix 01

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SERVICE BULLETIN

SUMMARY

**CONF ALL

FR1

FR20

190VT MODIFICATION OF THE WIRING IN 80VU

MODIFICATION OF 13VU

B_SB_222064_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 4

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SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 22

TITLE: AUTO FLIGHT - GENERAL - ACTIVATE STOP RUDDER INPUT

WARNING DEVICE

MODIFICATION No.: 13593S22853

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

310-203 310-221 310-222 310-304 310-308 310-324

(2) Effectivity by MSN

0162 0201 0217 0230 0233 0237 0241 0245 0248 0251 0254 0264 0267 0278 0281

0283 0288 0297 0313 0316 0318 0326 0331 0333 0335 0339 0343 0345-0346 0353

0355-0356 0359 0362 0364 0369 0378 0394 0439 0449 0452 0454 0456-0458 0467

0489 0492 0500 0534 0539 0542 0549 0552 0593 0638

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

99Y 0489

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SERVICE BULLETIN

OPERATOR MSN

FDX 0162 0201 0217 0230 0233 0237 0241 0245 0248 0251 0254 0264

0267 0278 0281 0283 0288 0297 0313 0316 0318 0326 0331 0333

0335 0339 0343 0345 0346 0353 0355 0356 0359 0362 0364 0369

0378 0394 0439 0449 0452 0454 0456 0457 0458 0467 0492 0500

0534 0539 0542 0549 0552 0593 0638

(4) Configuration by MSN

MSN CONFIGURATION

0162 0201 0217 0230 0233 0237 0241 0245 0248 0251 0254

0264 0267 0278 0281 0283 0288 0297 0313 0316 0318 0326

0331 0333 0335 0339 0343 0345 0346 0353 0355 0356 0359

0362 0364 0369 0378 0394 0439 0449 0452 0454 0456 0457

0458 0467 0489 0492 0500 0534 0539 0542 0549 0552 0593

0638

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 222064A01R01 1

B. CONCURRENT REQUIREMENTS

Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of

the following Service Bulletins :

Service Bulletin No. A310-22-2063

A310-22-2065

A310-31-2144

NOTE: Accomplishment of this Service Bulletin requires previously a crew training to

familiarize flight crew with the warning and the associated procedures.

C. REASON

(1) History

This Service Bulletin is issued further to an operator’s request.

(2) Objective/Action

Following report of events of excessive rapid alternating and large rudder pedal inputs

that resulted in high vertical stabilizer loads, this service bulletin provides increased

protection by improvement of the cockpit crew awareness in case of excessive rudder

reversal control input.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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SERVICE BULLETIN

This is achieved by activation of a warning red light "STOP" on rudder input panels in

front of each pilot which is reinforced by an aural warning "Stop rudder input".

This Service Bulletin installs on Captain and First Officer (F/O) side new 510VU

including a red lighted push-button and activates the function.

Aircraft have to be previously equipped with :

- System and mechanical provision

- Flight Warning Computer (FWC) STD S17 P/N 35-0B5-3008-320

- Flight Control Computer (FCC) P/N B470ADM03

(3) Advantages

Accomplishment of this Service Bulletin will satisfy the operator’s request.

(4) Operational/Maintenance Consequences

The Operational/Maintenance Consequences of this Service Bulletin are covered by the

update of the affected publications detailed in PLANNING INFORMATION

NOTE: Accomplishment of this Service Bulletin requires previously a crew

training to familiarize flight crew with the warning and the associated

procedures.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 222064-831-801-001: Modification

(1) Modify the Wiring in the Avionics Compartment.

(2) Modify the Equipment in the Glareshield Panel 13VU.

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA) will be issued

to confirm this classification. The accomplishment timescale, which has not yet been

defined, will be given in the AD.

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

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SERVICE BULLETIN

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 222064-831-801-001: Modification

Get Access 1.00

On Aircraft

Modify the Wiring in the Avionics Compartment. 2.00

Modify the Equipment in the Glareshield Panel 13VU. 1.00

Tests 1.00

Close-Up 1.00

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 4.00

NOTE: For detailed concerning the elapsed time assumptions, refer to Appendix 01 .

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +2.850 KG (+6.2831 LB)

Effect on Balance +26.163 KGM (+189.236 LB.FT )

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-31-53 06-41-00 06-41-52

06-41-53 20-21-12 21-21-00

22-10-00 22-18-34 22-27-00

22-40-00 24-00-00 24-31-11

24-41-00 31-51-00 33-12-00

33-13-00 33-14-00 52-10-00

52-30-00

Elec. Std. Practices Manual (ESPM) 20-25-51 20-52-10 20-55-00

Service Bulletin (SB) A310-22-2063

A310-22-2065

A310-31-2144

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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SERVICE BULLETIN

Standards Manual (SM)

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

K. PUBLICATION AFFECTED

Flight Crew Operating Manual (FCOM)

Flight Manual (FM)

Master Minimum Equipment List

This Service Bulletin has an operational impact. Please inform AIRBUS, at least four weeks in

advance, in case you need your operational documentation to be amended by a revision prior

to Service Bulletin embodiment. For this purpose, please request the revision by e-mail, online through the SB Reporting service or alternatively by fax to:

SEDOR4 - AIRBUS Customer Services Technical Data

Fax No.: (33) 5 61 93 28 06

E-mail: sb.reporting@airbus.com

SB Reporting service is accessible on-line through AIRBUSWorld from :

My on-line services’ section, available on all AIRBUSWorld pages

The Maintenance and Engineering Community, in :

- Modify and Upgrade page

- Access SB and VSB section.

These amendments will be confirmed by the next normal revision of operational

documentation, once your Service Bulletin accomplishment report has been sent, as usual, to

our Customer Services Aircraft In-Service Data (SEDOR4).

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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This Page Intentionally Left Blank

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Kit 222064A01R01 The AIRBUS material is included in the

commercial offer of the Letter Agreement,

and as such will be supplied by AIRBUS

Upgrade Services. To facilitate the material

reception, Airline Customers are requested to

send a Customer Purchase Order to:

AIRBUS Upgrade Services

Attn Key Account Manager (KAM)

(2) Price and Availability

Sales terms must be agreed between the Customer and AIRBUS in accordance with the

RFC (or RFC/RMO) procedure.

B. INDUSTRY SUPPORT INFORMATION

Refer to the paragraph : ’Price and Availability’.

C. LIST OF COMPONENTS

Kit 222064A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

2 A9550051000195 1 PANEL

3 A9550051000295 1 PANEL

E0171LA1202 2 CONTACT

EN3155-016M2018 6 CONTACT

EN3155-018M2018 2 CONTACT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

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F. TOOLING

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 222064-831-801-001 - Modification

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

Zone

120 210

Modified FIN

511VC2A 512VC2A 510VU1 510VU2

Access

Door 132AZ 811 831 841

Manpower

TOTAL MANHOURS 6.00

ELAPSED TIME (HOURS) 4.00

A. GENERAL

(1) Subtask 222064-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

(2) Subtask 222064-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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References

Aircraft Maintenance Manual (AMM) 06-31-53, Page Block 001

06-41-00, Page Block 001

20-21-12, Page Block 001

Elec. Std. Practices Manual (ESPM) 20-25-51

(a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001).

(b) For the identification of access panels (Refer to AMM 06-41-00, Page Block 001).

(c) Do a continuity test of the modified wires (Refer to ESPM 20-25-51).

B. PREPARATION

(1) Subtask 222064-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

24-00-00, Page Block 301

24-31-11, Page Block 401

52-10-00, Page Block 001

52-30-00, Page Block 001

(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page

Block 301).

(b) Put the access platforms in position at the level of door 831 or 841 and 811.

(c) Open the FWD passenger/crew door 831 or 841 (Refer to AMM 52-10-00, Page

Block 001 and AMM 06-41-52, Page Block 001).

(d) Open the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(e) Open the door 132AZ (Refer to AMM 06-41-53, Page Block 001).

(f) Make sure that the external connector(s) is (are) not connected to the aircraft

receptacle(s) EXT PW.

(g) Make sure that there is (are) warning notice(s) on external power receptacle to tell

persons not to connect an external power source.

(h) Make sure that the EMER EXIT LT pushbutton switch on 436VU is on DISARM

position.

(i) In the cockpit, on the overhead panel 424VU release BAT pushbutton switches.

(j) Put a warning notice on panel 424VU to tell persons not to operate the batteries.

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(k) Put a warning notice on the refuel/defuel panel 110VU to tell persons not to operate

the NORMAL BATTERY switch.

(l) Put a warning notice in the cockpit to tell persons not to start the APU.

(m) Put a warning notice in the cockpit to tell persons not to start the ENG 1 and 2.

(n) Battery disconnection :

- For Job Set-up, refer to the removal of the Batteries (Refer to AMM 24-31-11,

Page Block 401).

- Turn the knurled nut a quarter turn.

- Disconnect the connectors.

- Put blanking caps on the disconnected electrical connectors.

C. PROCEDURE

(1) Subtask 222064-831-001-001 - Modify the Wiring in the Avionics Compartment.

Work Zones and Access Panels

Zone Access/Work location

120 Access Door 132AZ, Door 811

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills ELECTRICAL

Material necessary to do the job

Kit 222064A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

E0171LA1202 2 CONTACT

EN3155-016M2018 6 CONTACT

EN3155-018M2018 2 CONTACT

References

Aircraft Maintenance Manual (AMM) 22-18-34, Page Block 401

Fig. A-FHAAA

Hook-up Chart of the Modification of the

Wiring in the Avionics Compartment.

Sheet 01

Fig. A-FHBAA

Hook-up Chart of the Modification of the

Wiring in 80VU.

Sheet 01

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References

Fig. A-FWAAA

Modification of the Wiring in the Avionics

Compartment.

Sheet 01

Sheet 02

Fig. A-FWBAA

Modification of the Wiring in 80VU.

Sheet 01

Sheet 02

(a) Remove the Flight Control Computers 301CA1 and 301CA2 (Refer to AMM

22-18-34, Page Block 401).

(b) Remove the wires as shown on the wiring diagram Fig. A-FWBAA Sheet 01 and as

given in the Hook-up Chart lines:

- 1 and 2 (Refer to Fig. A-FHBAA Sheet 01).

(c) Modify the wiring as shown in the wiring diagrams Fig. A-FWAAA Sheet 01, Fig. AFWAAA Sheet 02, Fig. A-FWBAA Sheet 01 and Fig. A-FWBAA Sheet 02, and as

given in the hook-up chart lines :

- 1 thru 8 (Refer to Fig. A-FHAAA Sheet 01),

- 6 thru 13 (Refer to Fig. A-FHBAA Sheet 01).

(d) If necessary, use :

6 Contact EN3155-016M2018

2 Contact EN3155-018M2018

2 Contact E0171LA1202

(e) Install the Flight Control Computers 301CA1 and 301CA2 (Refer to AMM 22-18-34,

Page Block 401) removed for access.

(2) Subtask 222064-831-002-001 - Modify the Equipment in the Glareshield Panel

13VU.

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831, Door 841

Work location Electrical panel 13VU

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills ELECTRICAL

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 12

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Material necessary to do the job

Kit 222064A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 A9550051000195 1 PANEL

3 A9550051000295 1 PANEL

References

Fig. A-FBAAA

Modification of the Equipment on the

Glareshield Panel 13VU

Sheet 01

Sheet 02

(a) On the glareshield panel 13VU :

1 Remove (Refer to Fig. A-FBAAA Sheet 01) :

2 Rest Plate A9251134100000 Item (1) Discard

2 Disconnect the connectors 511VC1A and 511VC2A from the LH rest plate

item 1 and the connectors 512VC1A and 512VC2A from the RH rest plate

item 1.

3 Install (Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02) :

FIN 510VU1

1 Panel A9550051000195 Item 2

FIN 510VU2

1 Panel A9550051000295 Item 3

4 Connect the connectors 511VC1A and 511VC2A to the panel 510VU1 item 2

and the connectors 512VC1A and 512VC2A to the panel 510VU2 item 3.

D. TEST

(1) Subtask 222064-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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References

Aircraft Maintenance Manual (AMM) 21-21-00, Page Block 501

22-10-00, Page Block 501

22-27-00, Page Block 501

22-40-00, Page Block 501

24-31-11, Page Block 401

24-41-00, Page Block 301

31-51-00, Page Block 501

33-12-00, Page Block 501

33-13-00, Page Block 501

33-14-00, Page Block 501

Elec. Std. Practices Manual (ESPM) 20-52-10

(a) Job Set-up

1 Battery re-connection

- For Job Set-up, refer to the installation of the Batteries (Refer to AMM

24-31-11, Page Block 401).

- Remove the blanking cap from the electrical connectors.

- Make sure that the electrical connectors are clean and in correct

condition.

- Connect the connector on the battery.

- Turn the knurled nut a quarter turn.

2 Remove all warning notices.

3 Restore the systems and the aircraft to normal operating condition.

(b) Procedure

1 Preliminary Tests

NOTE: If the aircraft is operated in CAT3 conditions, you must also do

the LAND test (Refer to AMM 22-40-00, Page Block 501).

a On each connector which was disconnected :

- Do the checks as defined by ESPM 20-52-10.

NOTE: The functional test and/or operational test requested by

this ESPM procedure is given hereafter.

b Do the operational test of the Annunciator Light Test (Refer to AMM

33-14-00, Page Block 501).

c Do the operational test of the General Illumination (Refer to AMM

33-12-00, Page Block 501).

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d Do the operational test of the Instrument and Panel Integral Lighting

(Refer to AMM 33-13-00, Page Block 501).

e Make certain that the ventilation system operates correctly (Refer to AMM

21-21-00, Page Block 501).

f Do the Automatic Flight System Test (Refer to AMM 22-40-00, Page

Block 501, para 1.A)

g Do the operational test of Electronic Centralized Aircraft Monitoring

/ Electronic Flight Instrument System Display Test (Refer to AMM

31-51-00, Page Block 501).

h Do the operational test FWC1 and FWC2 (Refer to AMM 31-51-00, Page

Block 501).

2 Test of the equipments (301CA1 and 301CA2)

a Do a detailed visual inspection of the autotrim function (Refer to AMM

22-27-00, Page Block 501, para 1.H).

b Do the autopilot operational test (Refer to AMM 22-10-00, Page Block

501, para 1.D Check of Pitch Trim Autotrim circuits).

3 Check the correct activation of the stop rudder input warning device as follows

:

a Job Set-up :

<1> Energize the aircraft electrical network (Refer to AMM 24-41-00,

Page Block 301).

<2> Make certain that electronic racks ventilation is correct.

<3> Make sure that the following circuit breakers are closed :

PANEL DESIGNATION FIN LOCATION SEE

NOTES

21VU AFS/AP1-FD1/FCC1/28VDC 306CA1 Ref. AMM

24-50-10

21VU AFS/AP2-FD2/FCC2/28VDC 306CA2 Ref. AMM

24-50-10

21VU ECAM/FWC1 7WW Ref. AMM

24-50-10

21VU ECAM/FWC2 32WW Ref. AMM

24-50-10

b Procedure :

ACTION RESULT

1. On overhead C/B panel 21VU :

- Open FCC2 circuit breaker 306CA2 and open

FWC2 circuit breaker 32WW.

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ACTION RESULT

2. On CAPT panel 510VU1 :

- Press STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that CAPT and F/O lights are illuminated.

Aural warning message "stop rudder input" is

repeated two times.

3. On CAPT panel 510VU1 :

- Release STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that both lights go off.

4. On overhead C/B panel 21VU :

- Close FWC2 circuit breaker 32WW and open

FWC1 circuit breaker 7WW.

5. On CAPT panel 510VU1 :

- Press STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that CAPT and F/O lights are illuminated.

Aural warning message "stop rudder input" is

repeated two times.

6. On CAPT panel 510VU1 :

- Release STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that both lights go off.

7. On overhead C/B panel 21VU :

- Close FCC2 circuit breaker 306CA2 and open

FCC1 circuit breaker 306CA1.

8. On F/O panel 510VU2 :

- Press STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that CAPT and F/O lights are illuminated.

Aural warning message "stop rudder input" is

repeated two times.

9. On F/O panel 510VU2 :

- Release STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that both lights go off.

10. On overhead C/B panel 21VU :

- Close FWC1 circuit breaker 7WW and open

FWC2 circuit breaker 32WW.

11. On F/O panel 510VU2 :

- Press STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that CAPT and F/O lights are illuminated.

Aural warning message "stop rudder input" is

repeated two times.

12. On F/O panel 510VU2 :

- Release STOP pushbutton switch.

On the glareshield panel 13VU :

- Check that both lights go off.

13. On overhead C/B panel 21VU :

- Close FWC2 circuit breaker 32WW and open

FCC1 circuit breaker 306CA1.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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4 Close-up :

a De-energize the aircraft electrical network (Refer to AMM 24-41-00, Page

Block 301).

E. CLOSE-UP

(1) Subtask 222064-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-41-52, Page Block 001

06-41-53, Page Block 001

52-10-00, Page Block 001

52-30-00, Page Block 001

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Close the door 132AZ (Refer to AMM 06-41-53, Page Block 001).

(c) Close the FWD cargo compartment door 811 (Refer to AMM 52-30-00, Page Block

001).

(d) Close the FWD passenger/crew door 831 841 (Refer to AMM 52-10-00, Page Block

001 and AMM 06-41-52, Page Block 001).

(e) Remove the access platforms.

(f) Restore the system and the aircraft to the normal operating condition.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 17

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**CONF ALL

BEFORE

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

A B A B

(1)

B_SB_222064_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Modification of the Equipment on the Glareshield Panel 13VU

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 18

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**CONF ALL

AFTER

LH SIDE SHOWN

RH SIDE SYMMETRICAL

B

3 RH

2 LH

STOP

RUDDER INPUTS

B_SB_222064_5_BAAA_02_03

Figure A-FBAAA - Sheet 02

Modification of the Equipment on the Glareshield Panel 13VU

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**CONF ALL

Figure A-FWAAA - Sheet 01

Modification of the Wiring in the Avionics Compartment.

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SERVICE BULLETIN

**CONF ALL

Figure A-FWAAA - Sheet 02

Modification of the Wiring in the Avionics Compartment.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 21

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**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 122 190VT 24G 3313−0611 R 2M PF18 122 371LF−A H M1O

 2 122 190VT 34G EN3155−016M2018 3313−0611 R 2M PF18 122 371LF−A H M1N

 3 122 190VT 1F 3313−0612 B 2M PF18 122 371LF−A J M1O

 4 122 190VT 35F EN3155−016M2018 3313−0612 B 2M PF18 122 371LF−A J M1N

 5 122 190VT WS 3313−1660 2M CF18 122 190VT 34K M1O

 6 122 190VT 24G EN3155−016M2018 3313−1660 2M CF18 122 190VT 34K M1N

 7 122 190VT WS 3313−1661 2M CF18 122 190VT 35K M1O

 8 122 190VT 1F EN3155−016M2018 3313−1661 2M CF18 122 190VT 35K M1N

 9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

24

25

 M1O = OLD HOOK−UP ON END 1

 M1N = NEW HOOK−UP ON END 1

Figure A-FHAAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in the Avionics Compartment.

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**CONF ALL

Figure A-FWBAA - Sheet 01

Modification of the Wiring in 80VU.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 23

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SERVICE BULLETIN

**CONF ALL

Figure A-FWBAA - Sheet 02

Modification of the Wiring in 80VU.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 24

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**CONF ALL

END1 LEAD END2

Instructions Zone or

Panel Elec.Ident. Term Terminal P/N

Wire

Ident. Co Rte Gauge

Lenght

mm Inch

Zone or

Panel Elec.Ident. Term Terminal P/N

L

i

n

e

 1 80VU 2297VC <C 2212−0014 W1M CF18 83VU 301CA1−AC 7 D

 2 80VU 2616VC JJ 2212−0069 X2M CF18 84VU 301CA2−AC 7 D

 3

 4

 5

 6 80VU 2297VC WS 2212−0350 CF18 80VU 123VT 73B M1O

 7 80VU 2297VC <C EN3155−018M2018 2212−0350 CF18 80VU 123VT 73B M1N

 8 80VU 2616VC WS 2212−0365 X2M CF18 80VU 124VT 22B M1O

 9 80VU 2616VC JJ EN3155−018M2018 2212−0365 X2M CF18 80VU 124VT 22B M1N

10 80VU 123VT WS 2212−0351 W1M CF18 83VU 301CA1−AC WS M1O+M2O

11 80VU 123VT 73A EN3155−016M2018 2212−0351 W1M CF18 83VU 301CA1−AC 7 E0171LA1202 M1N+M2N

12 80VU 124VT WS 2212−0366 X2M CF18 84VU 301CA2−AC WS M1O+M2O

13 80VU 124VT 22A EN3155−016M2018 2212−0366 X2M CF18 84VU 301CA2−AC 7 E0171LA1202 M1N+M2N

14

15

16

17

18

19

20

21

22

23

24

25

 M1O = OLD HOOK−UP ON END 1 M1N+M2N= NEW HOOK−UP ON END 1 AND 2

 M1N = NEW HOOK−UP ON END 1 D = DELETED WIRE

 M1O+M2O= OLD HOOK−UP ON END 1 AND 2

Figure A-FHBAA - Sheet 01

Hook-up Chart of the Modification of the Wiring in 80VU.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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**CONF ALL

Figure A-FWCAA - Sheet 01

Modification of the Wiring in 510VU1 (for information only).

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 26

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**CONF ALL

Figure A-FWDAA - Sheet 01

Modification of the Wiring in 510VU2 (for information only).

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 27

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This Page Intentionally Left Blank

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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Appendix 01

**CONF ALL

For detail concerning the elapsed time assumptions, refer to the Gantt chart shown below :

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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SERVICE BULLETIN

Appendix 01

**CONF ALL

ELAPSED TIME ASSUMPTIONS SERVICE BULLETIN No. A310−22−2064

TOTAL MANHOURS

SB ELAPSED TIME

6.00

4.00

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

MANHOURS GIVEN IN VENDOR SERVICE BULLETINS

ARE NOT REFLECTED IN THIS GANTT CHART.

01

02

NOTES:

:

:

SB ELAPSED TIME

(HOURS)

STEPS MH PER ET/S

0

GET ACCESS 1.00 1.00 1

CLOSE−UP 1.00 1.00 1

4 5

MODIFICATION WIRING 2.00 1.00 2 AVIONICS COMPARTMENT

MODIFICATION EQUIPMENT 13VU 1.00 1.00 1

TEST 1.00 1.00 1

1 2 3

B_SB_222064_5_AAAA_01_00

Figure A-FAAAA - Sheet 01

Elapsed Time Assumption

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

REVISION No.: 01 - May 31/12 Page: 2

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REPORTING SHEET

TITLE: AUTO FLIGHT - GENERAL - ACTIVATE STOP RUDDER INPUT

WARNING DEVICE

MODIFICATION No.: 13593S22853

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Nov 18/11 SERVICE BULLETIN No.: A310-22-2064

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